CN107444615B

CN107444615B - Combined elastic self-adaptive wing sweepback changing mechanism and control method

Info

Publication number: CN107444615B
Application number: CN201710276472.3A
Authority: CN
Inventors: 董彦非; 余斌高
Original assignee: Xian Aeronautical University
Current assignee: Xian Aeronautical University
Priority date: 2017-04-25
Filing date: 2017-04-25
Publication date: 2019-12-20
Anticipated expiration: 2037-04-25
Also published as: CN107444615A

Abstract

A combined elastic self-adaptive wing sweepback varying mechanism and a control method thereof are provided, wherein a fixed guide rod is positioned in the center of a shell, and the outer circumferential surface of a connecting disc at one end of the fixed guide rod is in threaded connection with the inner surface at one end port of the shell. The rolling guide sleeve is sleeved at the other end of the fixed guide rod. The inner end of the movable guide rod is sleeved on the fixed guide rod and the rolling guide sleeve, and the inner surface of the movable guide rod is in clearance fit with the outer surface of the fixed guide rod and the outer surface of the rolling guide sleeve; the inner surface of the outer end of the movable guide rod is in threaded connection with the outer surface of the joint. And wing connecting joint bearing mounting holes are distributed at the outer end of the joint. The invention reduces driving elements such as a control computer, a hydraulic system and the like, so that the whole sweepback-changing mechanism has light weight; and the realization of the control law is completely realized by a mechanical device with a longer service life, and compared with electronic equipment, the reliability is high.

Description

Combined elastic self-adaptive wing sweepback changing mechanism and control method

Technical Field

The invention relates to the field of aircraft design, in particular to a combined elastic self-adaptive wing sweepback changing mechanism.

Background

The airplane adopting the variable sweepback wings is always an important airplane design structure due to the fact that aerodynamic requirements of low-speed flight and high-speed flight of the airplane can be better considered, such as American F-14, F-111 and B-1B, and American Mige-23 of the former Soviet Union. The variable sweepback wing schemes of the airplanes are mostly finished by adopting an electric control hydraulic driving mode, namely, according to the requirements of the flying speed and the flying height, a control computer sends out a control instruction, and a hydraulic servo device finishes the driving control of the sweepback angle of the wing. In these airplanes, because of the need of changing the sweepback angle of the wing, a heavier and more complicated variable speed transmission device is structurally arranged, and meanwhile, a hydraulic mechanism is needed to drive the sweepback wing to move, so that the weight of the airplane is increased more.

Because the advantages of the variable-sweepback wing aircraft are outstanding, the research on the structure of the variable-sweepback wing is a hot point for the design of the aircraft. For example, a telescopic morphing wing transmission mechanism (publication number CN101857084A) applied by Zwein et al of northwest industrial university designs that a speed reducing mechanism is driven by an electric mechanism to realize the change of the sweepback angle of the wing. For another example, a patent (publication number CN101028866) reported by wilbin industrial university coolness pine et al designs a control device which uses memory alloy as a driving energy source to drive a corresponding mechanism to complete the control of the sweepback angle of the wing. These configurations no longer use hydraulic energy as the power for the variable sweep wing drive, thereby structurally reducing the weight of the hydraulic system components accessories, but still require electrical mechanisms or controls, i.e., additional weight with a partial energy component.

Disclosure of Invention

In order to overcome the defect of heavy structure in the prior art, the invention provides a combined elastic self-adaptive wing sweepback changing mechanism and a control method.

The invention comprises a shell, a joint, a small spring adjusting threaded sleeve, a metal diaphragm capsule, a spring seat, a support sleeve, a small spring adjusting taper sleeve, a large spring adjusting taper sleeve, a small spring, a rolling guide sleeve, a movable guide rod, a large spring, an outer shell, a fixed guide rod and a pressure regulating valve. The fixed guide rod is positioned in the center of the shell, and the outer circumferential surface of the connecting disc at one end of the fixed guide rod is in threaded connection with the inner surface at one end port of the shell. The rolling guide sleeve is sleeved at the other end of the fixed guide rod. The inner end of the movable guide rod is sleeved on the fixed guide rod and the rolling guide sleeve, and the inner surface of the movable guide rod is in clearance fit with the outer surface of the fixed guide rod and the outer surface of the rolling guide sleeve; the inner surface of the outer end of the movable guide rod is in threaded connection with the outer surface of the joint. And wing connecting joint bearing mounting holes are distributed at the outer end of the joint.

The spring seat is sleeved on the circumferential surface of the movable guide rod, the inner surface of the inner end of the spring seat is in clearance fit with the outer surface of the movable guide rod, and the end surface of the outer end of the spring seat is fixedly connected with the inner end surface of the metal film box base sleeved on the small spring adjusting screw sleeve;

four lugs evenly distributed on the outer circumference of the middle part of the spring seat are respectively embedded into four sliding grooves on the inner surface of the other end of the shell, so that the sliding grooves are in clearance fit.

The large spring is sleeved on the outer circumferential surfaces of the movable guide rod and the fixed guide rod, the end face of one end of the large spring is attached to the inner end face of the connecting disc on the fixed guide rod, the other end of the large spring is located in a circular cavity between the outer circumferential surface of the small-diameter end of the spring seat and the inner surface of the shell, and the end face of the end is attached to the outer end face of the middle part of the spring seat. The small spring is sleeved on the movable guide rod, the end face of the small spring is attached to the inner end face of the small-diameter end of the spring seat, and the other end of the small spring is attached to the inner end face of the small spring adjusting threaded sleeve sleeved at one end, connected with the joint, of the fixed guide rod. The small spring adjusting taper sleeve is positioned in the small-diameter end of the spring seat, and four arc-shaped inserting blocks on the small spring adjusting taper sleeve are respectively installed in four arc-shaped inserting grooves on the end face of the small-diameter end of the spring seat. The large spring adjusting taper sleeve is sleeved on the outer surface of the small-diameter end of the spring seat, and one end of the large spring adjusting taper sleeve is fixed on the outer end face of the middle part of the spring seat. One end of the supporting sleeve is sleeved on the outer surface of the inner end of the small spring adjusting screw sleeve and is fixed on the inner end surface of the metal diaphragm box; the outer surface of the flange of each arc supporting plate end at the other end of the supporting sleeve is respectively contacted with the inner surface of the large spring adjusting taper sleeve, and the inner surface of each flange is respectively contacted with the outer surface of the small spring adjusting taper sleeve.

The metal bellows is communicated with the pressure regulating valve through a guide pipe.

The pressure regulating valve is positioned outside the shell. The pressure regulating valve comprises a main valve body, a guide valve body, a main valve core, a guide valve seat, a guide valve needle, a spring, an air guide pipe, a membrane and a high-pressure air tank. Wherein: the guide valve seat is positioned in the mounting hole at one end of the guide valve body, and the guide valve needle is mounted in a groove in the center of the end face at the other end of the guide valve body; the conical end of the guide valve needle is inserted into a central hole on the guide valve seat; and a reinforcing plate is fixed on the outer end face of one end plate of the pilot valve needle. The diaphragm divides the space between the reinforcing plate and the end plate of the pilot valve needle into two cavities. The spring is divided into an upper spring and a lower spring, the lower spring is sleeved on the outer circumferential surface of the pilot valve needle, one end of the lower spring is attached to the inner end face of the large-diameter section of the pilot valve needle, and the other end of the lower spring is attached to the bottom surface of the groove; the upper spring is positioned at the outer end of the pilot valve needle, one end of the upper spring is attached to the inner end face of the pilot valve cover, and the other end of the upper spring is attached to the outer end face of the reinforcing plate. The main valve body is mounted on the side surface of the end of the pilot valve body having the pilot valve seat. The main valve core is positioned in the main valve body, the outer circumferential surface of the large-diameter end of the main valve core is in clearance fit with the inner surface of the main valve body, and the outer circumferential surface of the small-diameter end of the main valve core is in clearance fit with the groove wall of the circumferential surface of the pilot valve body; two ends of the small hole in the center of the main valve core are respectively communicated with the small hole in the main valve body and the small hole at the bottom of the groove of the pilot valve body. A spring is placed in an inner hole of the small-diameter end of the main valve body. The high-pressure air tank is communicated with the main valve body through an air duct, and high-pressure air is introduced into the lower cavity of the main valve core to form a main air flow channel.

The inner surface of the main valve seat end cover is provided with a boss protruding axially, the center of the boss is provided with a conduit mounting hole penetrating axially, and the inner end orifice of the mounting hole is conical and matched with the conical section on the main valve core. The circumference of one end of the main valve seat, which is provided with an end cover, is provided with a radial through hole for installing an air duct. The end face of the outlet end of the main valve seat is in a step shape, and a positioning spigot matched with the outer surface of the pilot valve body is formed.

One end of the main valve core is a cylindrical section matched with the sleeve on the pilot valve body, and the other end of the main valve core is a conical section; and a disc is arranged between the cylindrical section and the conical section, and the outer surface of the disc is in clearance fit with the inner surface of the small-diameter hole of the main valve seat. The inner diameter of the cylinder section is slightly larger than the outer diameter of the main valve spring. The conical section is in sealing fit with the inner end of the mounting hole on the main valve seat; the center of the conical section is provided with an air hole which is axially communicated.

One end of the guide valve needle is a disc riveted with the diaphragm, the other end of the guide valve needle is a needle rod, and the front end of the needle rod is a conical needle head. The needle head is in clearance fit with the central hole of the guide valve body and forms a guide valve part with the opening on the guide valve seat so as to control the communication and the separation of the inlet and outlet pressures of the main valve core.

The main body of the guide valve body is cuboid. The circular end plate is matched with the pilot valve cover at one end of the main body, a groove is formed in the center of the outer end face of the circular end plate, and a through hole of a pilot valve needle rod extending along the length direction of the pilot valve body is formed in the center of the groove. And the geometric center of the other end of the guide valve body is provided with a mounting hole. The pilot valve seat mounting hole is coaxial with and communicated with the through hole of the pilot valve needle rod. The outer surface of one side of the pilot valve body is provided with a sleeve protruding out of the outer surface, and the inner diameter of the sleeve is in clearance fit with the outer circumferential surface of the small outer diameter end of the main valve core.

The port of the large-diameter section one end of the spring seat is open, and the port of the small-diameter section one end of the spring seat is provided with an end plate. The inner diameter of the large-diameter end is the same as the outer diameter of the metal diaphragm box base; the small-diameter end is provided with an end plate, and the inner diameter of the small-diameter end is the same as the maximum outer diameter of the small-spring adjusting taper sleeve. Four radially protruding bosses are uniformly distributed on the outer circumferential surface of the spring seat and are positioned at the step in the middle of the outer circumferential surface of the spring seat; each boss corresponds to four grooves uniformly distributed on the circumferential surface of the shell. And a through hole in clearance fit with the outer circumferential surface of the movable guide rod is formed in the center of the end face of the small-diameter end of the spring seat. Four arc through grooves are formed in the end face of the small-diameter end of the spring seat, the four arc through grooves surround the through holes and are uniformly distributed, and the arc strip end of one end of the small spring adjusting taper sleeve penetrates through the end plate of the spring seat from each arc through groove. 4 slots matched with the insertion blocks of the large spring adjusting taper sleeves are uniformly distributed on the outer end face of the middle part of the spring seat; and the inner side of the slot is provided with a mounting hole. Three trapezoidal grooves extending to the end of the small-diameter section along the axial direction are uniformly distributed on the end face between the large-diameter section and the small-diameter section, and the shape of the inner cavity of each trapezoidal groove is matched with the shape of each support rod on the support sleeve and serves as a sliding groove for the movement of each support rod.

The supporting sleeve is cylindrical, and one end of the supporting sleeve is connected with the metal diaphragm box; the flange at the other end extends out to a certain thickness and is respectively attached to the outer conical surface of the small spring adjusting taper sleeve and the inner conical surface of the large spring adjusting taper sleeve on the inner side. The bearing mounting end of the supporting sleeve is annular, and the other end of the supporting sleeve is axially divided into three arc slats; the end surfaces of the three arc-shaped strips are provided with flanges protruding in the radial direction, and the outer surfaces and the inner surfaces of the flanges are respectively contacted with the inner surface of the large spring adjusting taper sleeve and the outer conical surface of the small spring adjusting taper sleeve simultaneously.

The small spring adjusting taper sleeve is in a thin-wall cylindrical shape and is divided into a connecting section, a taper section and a deformation section, wherein the taper section and the deformation section are connected through the connecting section, and the small diameter end of the taper section is connected with the connecting section. The taper of the taper section is 10 degrees, and the maximum outer diameter is the same as the inner diameter of the support sleeve. Three separation grooves are formed in the axial direction of the conical section, extend from the end head of the conical section to the joint of the conical section and the connecting section, and divide the conical section into three arc plates in the axial direction. The inner surface of each block of the conical section is a helical surface, and the pitch of the helical surface is equal to 10 mm. The outer diameter of the deformation section is equal. Four deformation grooves with the width of 10mm are formed in the axial direction of the deformation section, the deformation grooves extend from the end of the deformation section to the joint of the deformation section and the connecting section, the deformation section is axially divided into four arc-shaped strips, and the arc-shaped strips can penetrate through the arc-shaped grooves in the spring seat and are fixed through round nuts. The outer surface of each arc-shaped lath of the deformation section is a thread surface.

The large spring adjusting taper sleeve is in a thin-wall cylindrical shape and consists of a circular ring section and a taper section. And connecting screw holes are distributed on the end surface of the circular ring section. The taper of the conical section is 10 degrees. The outer surface of the conical section is a spiral surface, the thread pitch on the spiral surface is 15mm, and the inner surface of the conical section is in contact with the outer rim of the support sleeve, wherein the thread pitch is the same as the lead of the pre-compressed large spring. Three uniformly distributed deformation grooves are processed on the conical section along the axial direction.

The outer circumferential surface of the movable guide rod is in a step shape, the circumferential surface of the small outer diameter section at one end is a threaded surface, and the other end of the movable guide rod is a limiting boss protruding in the radial direction; the middle part of the movable guide rod is a working section of the movable rod. The inner diameter of the movable guide rod is in clearance fit with the outer diameter formed by the balls fixed on the rolling guide sleeve and the outer diameter of the working section of the fixed guide rod; rolling friction is formed between the movable guide rod and the balls of the rolling guide sleeve. The inner circumferential surface of the small outer diameter section of the movable guide rod is an internal thread surface connected with the joint.

The diameter of the small-diameter end of the fixed guide rod is slightly smaller than the minimum inner diameter formed by the balls on the rolling guide sleeve; the circumferential surface of one end, matched with the rolling guide sleeve, of the fixed guide rod is a threaded surface. The large-diameter end of the other end of the fixed guide rod is a rod body of the guide rod, the end head of the outer end of the rod body is provided with a connecting disk protruding in the radial direction, and the circumferential surface of the connecting disk is a threaded surface matched with the internal thread of the shell. The end face of the outer end of the rod body is provided with a connecting plate which extends axially, a bearing mounting hole of the fuselage fixed joint is formed in the connecting plate, and the center line of the bearing mounting hole of the fuselage fixed joint after assembly is parallel to the center line of the bearing mounting hole of the wing connecting joint of the joint at the other end.

The invention provides a specific process for implementing control by utilizing the combined elastic self-adaptive wing sweepback changing mechanism, which comprises the following steps:

step 1, connecting the combined elastic self-adaptive wing sweepback changing mechanism with a fuselage and a wing.

The wing transmission rod is fixedly connected with a joint on the combined elastic self-adaptive wing sweepback changing mechanism through a bearing 1, and a fuselage joint is in supporting connection with a fixed guide rod on the combined elastic self-adaptive wing sweepback changing mechanism through two bearings.

Step 2, setting the initial state of the combined elastic self-adaptive wing sweepback changing mechanism:

the small spring is used for adjusting the threaded sleeve to enable the pretightening force of the small spring to reach the aerodynamic resistance with the flight speed of 0.4 Mach; the pretightening force of the large spring is controlled to be the pretightening force when the small spring is completely compressed by adjusting the threaded sleeve through the spring seat. The pre-tightening force of the small spring when the small spring is completely compressed is determined by design. The determined initial pretightening force is required to meet the condition that the pilot valve is fully opened under the ground condition; along with the change of flying height, the linear turn-off of the pilot valve is reduced, the diaphragm moves to the side of the pilot valve cover to the limit position, the pilot valve needle is driven to be opened to the maximum, the pilot valve is in a full-open state, the gas pressure behind the adjusted main valve core is the maximum pressure, the controlled metal diaphragm box is in a full-expansion state, and the support sleeves are all in the limit position towards the fixed guide rod; pushing the support sleeve to the limit position on one side of the fixed guide rod, so that the large spring adjusting taper sleeve is completely contracted, and the deformable number of turns of the large spring is minimized; meanwhile, the small spring adjusting taper sleeve is completely opened, and the deformable number of turns of the small spring becomes the maximum.

And 3, controlling when the flight Mach number is less than 0.4:

when the flight mach number is less than 0.4, all the wing sweep angles in the flight speed range are the designed initial angles.

And 4, controlling when the flight Mach number is larger than 0.4:

when the flight Mach number is larger than 0.4, the spring in the wing combination elastic self-adaptive wing sweepback changing mechanism starts to be compressed to enable the movable guide rod to move towards the fixed guide rod side, and the controlled wing sweepback angle is changed into two sections:

i first section

When the flying height of the airplane is less than 4000 meters: when the Mach number is increased from 0.4 to less than 0.6, the small spring in the combined elastic adaptive wing sweep-back mechanism is compressed, so that the joint moves towards one side of the fixed guide rod of the adaptive wing sweep-back mechanism, and the wing sweep angle is controlled to be increased from 10 degrees to 20 degrees.

When the flying height of the airplane is more than or equal to 4000 meters and less than or equal to 10000 meters: the external air pressure is reduced, the deformable number of turns of the small spring in the combined elastic self-adaptive wing sweepback-changing mechanism is reduced, and the rigidity of the small spring control section is increased; simultaneously, the large spring adjusting taper sleeve gradually expands under the elastic action of the large spring adjusting taper sleeve, so that the number of fitting turns of the large spring and the large spring adjusting taper sleeve is reduced, the actual number of deformation turns of the large spring is increased, and the rigidity of the large spring control section is reduced. When the Mach number is increased from 0.4, the control sweep angle change slope when the small spring is compressed is increased, and the small spring is completely compressed until the flying speed is more than 0.6. In the process, the moving distance of the support sleeve depends on the air pressure change caused by the flying height, the higher the flying height is, the smaller the air pressure is, the smaller the pilot valve is closed, the longer the distance for controlling the support sleeve to move towards the joint direction is, the more the rigidity of the small spring is increased, the higher the flying speed when the sweepback angle change of the corresponding wing is turned is, and the smaller the sweepback angle when the wing is turned is, namely 20-16 degrees.

When the flying height of the airplane is more than 10000 meters: the pressure of the side of a diaphragm pilot valve of a pressure regulating valve in the combined elastic self-adaptive wing sweepback changing mechanism is reduced, a main valve core is also closed, and the pressure of gas regulated by the main valve is gradually reduced. The metal diaphragm box contracts along the axial direction to drive the supporting sleeve to move to the limit position of the other side of the stroke of the supporting sleeve in the direction of the joint, the small spring adjusts the taper sleeve to completely contract, and the deformable number of turns of the small spring is reduced to the minimum; meanwhile, the large spring adjusting taper sleeve is completely opened, so that the actual deformation circle number of the large spring is increased to the maximum. When the mach number is increased from 0.4, the slope of the change of the sweep angle controlled when the small spring is compressed increases, compared to a height of 10000 meters or less, due to the increase in the stiffness of the small spring, until the flying speed reaches 0.8, the small spring will be fully compressed, corresponding to a sweep angle of 16 °.

II second section

The sweepback angle change of the wing is controlled by the supporting sleeve.

When the flying height of the airplane is less than 4000 meters: when the Mach number is increased from 0.6 to less than 0.9, the small spring in the combined elastic self-adaptive wing variable sweepback mechanism is completely compressed, the large spring starts to be compressed, so that the joint continues to move, the sweepback angle is controlled to continue to increase according to the slope controlled by the large spring, and the corresponding relation between the flight Mach number from 0.6-0.9 and the sweepback angle of the wing from 20 degrees to 60 degrees is realized.

When the flying height of the airplane is more than or equal to 4000 meters and less than or equal to 10000 meters: when the corresponding sweepback angle is increased from 20 degrees to 60 degrees at 4000 meters, the change of the flying speed is Mach 0.6 to 0.9; when the corresponding sweepback angle is increased from 16 degrees to 60 degrees at 10000 meters, the change of the flying speed is Mach 0.8 to 0.9; and the initial angle of the sweepback angle is linearly changed between 20 degrees and 16 degrees when the flying height is 4000 meters to 10000 meters, and the corresponding flying speed change is also changed between Mach 0.6 to 0.8.

When the flying height of the airplane is more than 10000 meters: when the Mach number is increased from 0.8 to less than 0.9, the small spring in the adaptive wing variable sweepback mechanism is completely compressed, the large spring is compressed, and the effective deformation number of turns of the large spring is increased to the maximum, and the rigidity of the large spring is reduced to the minimum, so that the corresponding sweepback angle is 16-60 degrees when the flying speed reaches the Mach number of 0.8-0.9.

The invention carries out innovative design aiming at the characteristics of complex structure, heavy weight and the like of the existing variable sweepback wing structure design which needs external energy units such as hydraulic pressure and the like and units such as a control computer and the like. The flight resistance acting on the wing in the flight process is taken as a driving energy for changing the sweepback angle of the wing, and a speed self-adaptive sweepback wing changing structure is reasonably designed, so that the flight resistance controls the mechanism to move, the sweepback angle is further controlled, and the corresponding relation between the flight speed and the sweepback angle is realized; meanwhile, the mechanism can also adaptively control different gears of the variable-sweep wing structure according to different flying heights, so that the corresponding relation between the flying speed and the sweep angle under different flying heights is realized.

According to the change requirements of the sweepback angle, the flying speed and the flying height, the invention realizes the change rule shown in the attached figure 1 and can obtain better effect. Wherein:

1. when the flight Mach number is less than 0.4, the sweep angle of the wing keeps the initial angle;

2. flight mach number greater than 0.4:

when the flying height is less than 4000 meters, the change rule of the wing sweep angle along with the flying speed is shown as broken lines 51 and 52 in the attached figure 1. Namely: during the increase of the flight Mach number from 0.4 to 0.6, the change of the sweepback angle is linearly increased from the initial design angle of 10 degrees to 20 degrees as shown by a broken line segment 51 in the attached figure 1; during the continuous increase of the flight mach number from 0.6 to 0.9, the change of the sweep angle is linearly increased from 20 ° to 60 ° as shown by a broken line segment 52 in fig. 1;

when the flying height is more than 10000 m, the change rule of the sweep angle along with the flying speed is shown as broken lines 53 and 54 in fig. 1. Namely: during the increase of the flight mach number from 0.4 to 0.8, the change of the sweep angle is linearly increased from the initial angle to 16 ° as shown by the broken line segment 53 in fig. 1; during the continuous increase of the flight mach number from 0.8 to 0.9, the change of the sweep angle is linearly increased from 16 ° to 60 ° as indicated by the broken line segment 54 in fig. 1;

when the flying height is 4000 to 10000 m, the flying speed corresponding to the turning angle of the sweepback angle change of 20 to 16 degrees is adjusted steplessly according to the flying height between mach 0.6 and mach 0.8, namely the flying height is different, and the corresponding turning points of the broken line are different.

From the foregoing control requirements, it can be seen that the change between the wing sweep angle and the flying speed is typically a piecewise function, and exhibits two different linear relationships throughout the entire range of change. Meanwhile, the position of the middle turning point of the linear relation changes along with the change of the flying height, and the characteristics of a broken line family are presented on the whole.

1. Realization of broken line rule between flying speed and sweepback angle

Based on the characteristics, the invention realizes two-stage different linear relation between the sweepback angle and the flying speed by combining the elastic self-adaptive wing sweepback changing mechanism, as shown in figure 2. The mechanism is fixed with a machine body through a joint at the side of a fixed guide rod by a bearing, and the pneumatic resistance load of the wing is transferred to a small spring adjusting threaded sleeve through the joint and a movable guide rod to compress the small spring to deform; when the small spring is gradually compressed to the limit and the pneumatic resistance is continuously increased, the pneumatic load is applied to the large spring through the compressed small spring and the spring seat, so that the large spring is compressed, and the joint and the movable guide rod are continuously retracted. Because the big spring and the small spring have different rigidity, the corresponding relation of two sections of different slopes is realized between the pneumatic load and the retraction stroke of the joint.

2. Realization of law (broken line family) between flying speed and sweepback angle when flying height changes

In fig. 1, when the flight altitude is higher, the position of the middle turning point of the broken line moves upwards, that is, the flight speed corresponding to the sweep back angle of 10-20 ° is required to be higher, and the flight speed range corresponding to the sweep back angle of 16-60 ° is required to be smaller.

The present invention senses the flying height change by a pressure regulating valve in which a diaphragm divides a cavity portion enclosed by a pilot valve cover and a pilot valve body into two parts, and if a constant pressure is maintained to a space on the pilot valve cover side, the space on the pilot valve body side is communicated with the outside atmosphere. Through the reasonable design of the springs on the two sides, when the ground is high, the pressures on the two sides of the diaphragm are unbalanced, so that the diaphragm drives the pilot valve riveted on the diaphragm to move towards the side of the pilot valve cover, and the pilot valve is in a completely opened state. In this case, the gas above the main valve can be quickly released through the pilot valve, and the main valve is also in a full open state by the pressure difference between the upper and lower sides of the main valve body. The high-pressure air from the high-pressure air tank is regulated by the main valve to be at the maximum pressure, and the air enters the metal diaphragm box to ensure that the metal diaphragm box is completely expanded along the axial direction to drive the support sleeve to axially move to the limit position, so that the large spring adjusting taper sleeve is at the minimum and the small spring adjusting taper sleeve is at the maximum, and the number of effective turns of the large spring which can be deformed is reduced to the minimum and the number of effective turns of the small spring which can be deformed is the maximum. When the flying height of the outside rises, the external air pressure is reduced, so that the pressure on the side of the membrane guide valve is reduced, the guide valve needle gradually moves towards the guide valve body under the action of the pressure difference on two sides of the membrane, the guide valve is gradually closed, the pressure above and below the main valve core is controlled to change, the main valve core is also gradually closed, and the gas pressure after the main valve is controlled to be gradually reduced. The metal diaphragm box is contracted along the axial direction to drive the support sleeve to move axially, so that the small spring is forced to adjust the taper sleeve to contract, and a part of small spring ring is controlled to be attached to the fixed taper sleeve, so that the deformable number of turns of the small spring is reduced; meanwhile, the large spring adjusting taper sleeve gradually expands under the action of elasticity of the large spring adjusting taper sleeve, so that the number of joint turns of the large spring and the large spring adjusting taper sleeve is reduced, the actual number of deformation turns of the large spring is increased, the rigidity of the small spring control section is increased, the rigidity of the large spring control section is reduced, and the two sections of control slopes can be ensured to change along with the flying height as long as different axial positions of the support sleeve are controlled according to the flying height. Thus, the law that the flight speed corresponding to the sweep angle of 10-12 degrees is increased and the flight speed corresponding to the sweep angle of 12-60 degrees is narrowed is realized.

It can be seen that in the implementation of the invention, the energy for driving the wing to change in the sweepback angle is derived from flight resistance, and is not dependent on externally provided hydraulic energy or electric energy. Meanwhile, the whole control process of the change of the sweepback angle of the wing is completely automatically balanced by the change of the pneumatic resistance and the compression amount of the large spring and the small spring in the combined elastic self-adaptive sweepback mechanism of the wing, no electric signal is transmitted and controlled, and a control computer and related hardware equipment are omitted.

Compared with the prior art, the combined elastic self-adaptive wing sweepback changing mechanism has at least two advantages: firstly, the whole sweepback-changing mechanism has light weight because of reducing driving elements such as a control computer, a hydraulic system and the like; and secondly, the realization of the control rule is completely realized by a mechanical control mechanism with a longer service life, and compared with electronic equipment, the reliability is high.

It can be seen that the greatest difference between the present invention and the prior art is that the driving energy of the sweepback angle of the wing comes from the flight resistance acting on the wing during flight, and no external energy source is required to provide the driving power. The difference between the invention and the prior art is that the control of the wing sweep angle does not adopt the control of an electric signal, and the adjustment of the wing sweep angle is automatically realized by the change of flight resistance and the designed combined elastic self-adaptive wing sweep-variable mechanism.

Drawings

FIG. 1 is a rule that a sweepback angle changes with Ma and height states in the flight process;

FIG. 2 is a front view of the present invention;

fig. 3 is a side view of the mechanical control mechanism of the present invention.

FIG. 4 is a left side view of FIG. 2;

FIG. 5 is a right side view of FIG. 2;

FIG. 6 is a schematic structural view of the pressure regulating valve;

FIG. 7 is a schematic diagram of the combination of a spring seat, a brace, a small spring adjustment taper sleeve, a large spring adjustment taper sleeve, a small spring, and a metal bellows;

FIG. 8 is a schematic structural view of the joint, wherein 8a is a front view and 8b is a view from A-A of 8 a;

FIG. 9 is a schematic view of the construction of the small spring adjustment screw insert, wherein 9a is a front view and 9b is a left side view of 9 a;

FIG. 10 is a schematic structural view of a metal bellows base, wherein 10a is a front view and 10b is a left side view of 10 a;

FIG. 11 is a schematic structural view of a metal bellows, wherein 11a is a front view, and 11b is a left side view of 11 a;

FIG. 12 is a schematic view of the construction of the main valve seat, wherein 12a is a front view, 12b is a left side view of 12a, and 12c is a top view of 12 a;

FIG. 13 is a schematic structural view of a pilot valve cover; wherein 13a is a front view and 13b is a left side view of 13 a;

FIG. 14 is a schematic diagram of a membrane junction; wherein 14a is a front view and 14b is a left side view of 14 a;

FIG. 15 is a schematic view of the construction of the pilot valve pin; wherein 15a is a front view and 15b is a left side view of 15 a;

FIG. 16 is a schematic view of the structure of the pilot valve body; where 16a is the front view, 16b is the left side view of 14a, 16, c is the top view of 164 a;

FIG. 17 is a schematic of the main spool construction; wherein 17a is a front view and 17b is a top view of 17 a;

FIG. 18 is a schematic view of the spring seat adjustment nut; wherein 18a is a front view and 18b is a left side view of 18 a;

FIG. 19 is a schematic view of a spring seat; where 19a is a front view and 19b is a left side view of 19 a;

FIG. 20 is a schematic view of the construction of the brace; wherein 20a is a front view and 20b is a left side view of 20 a;

FIG. 21 is a schematic view of the structure of a small spring adjustment cone; wherein 21a is a front view and 21b is a left side view of 21 a;

FIG. 22 is a schematic view of the structure of a large spring adjustment cone; wherein 22a is a front view and 22b is a left side view of 22 a;

FIG. 23 is a schematic view of the construction of the roller guide sleeve;

FIG. 24 is a schematic view of the construction of the movable guide bar;

fig. 25 is a schematic structural view of the outer case, in which 25a is a front view and 25b is a left side view of 25 a;

FIG. 26 is a schematic view of the structure of the fixed guide bar, in which 26a is a front view and 26B is a view from the B-B direction of 26 a.

In the figure:

1. the wing is connected with a joint bearing; 2. a joint; 3. a movable guide rod lock nut; 4. a small spring adjusting screw sleeve locking nut; 5. a small spring adjusting screw sleeve; 6. a metal bellows base; 7. a capsule base set screw; 8. a metal bellows set screw; 9. a metal bellows; 10. the supporting sleeve fixes the screw; 11. sealing the felt ring; 12. a strut return spring; 13. a supporting sleeve sealing felt ring; 14. the big spring adjusts the taper sleeve fixing screw; 15. a main valve seat; 16. a nut; 17. a spring washer; 18. a bolt; 19. a pilot valve cover; 20. an upper spring; 21. a reinforcing plate; 22. riveting; 23. a membrane; 24. a high pressure gas tank; 25. an air duct; 26. a lower spring; 27. a guide valve needle; 28. a pilot valve body; 29. a guide valve seat; 30. a main valve spring; 31. a sealing gasket; 32. a main valve element; 33. a spring seat adjusting threaded sleeve; 34. a connecting disc; 35. a spring seat; 36. supporting sleeves; 37. a small spring adjusting taper sleeve; 38. a large spring adjusting taper sleeve; 39. a small spring; 40. an elastic washer; 41. a round nut; 42. a rolling guide sleeve stop nut; 43. a rolling guide sleeve; 44. a movable guide rod; 45. a large spring; 46. an outer housing; 47. fixing the guide rod; 48. the machine body is fixed with a joint shaft.

Detailed Description

Example 1

The embodiment is a combined elastic self-adaptive wing sweepback changing mechanism which comprises a mechanical control mechanism and a pressure regulating valve.

The mechanical control mechanism comprises: the valve comprises a connector 2, a small spring adjusting screw sleeve 5, a metal diaphragm box 9, a strut return spring 12, a main valve seat 15, a guide valve cover 19, an upper spring 20, a diaphragm 23, a lower spring 26, a guide valve needle 27, a guide valve body 28, a guide valve seat 29, a main valve core 32, a spring seat adjusting screw sleeve 33, a spring seat 35, a support sleeve 36, a small spring adjusting taper sleeve 37, a large spring adjusting taper sleeve 38, a small spring 39, a rolling guide sleeve 43, a movable guide rod 44, a large spring 45, an outer shell 46 and a fixed guide rod 47. The housing 46 is the carrier of this embodiment. Wherein, a fixed guide rod 47 is positioned at the center in the shell, and the outer circumferential surface of the connecting disc 34 at one end of the fixed guide rod is in threaded connection with the inner surface at one end port of the shell. A roller guide 43 is sleeved on the other end of the fixed guide rod and is positioned by a roller guide retaining nut 42. The inner end of the movable guide rod 44 is sleeved on the fixed guide rod 47 and the rolling guide sleeve 43, and the inner surface of the movable guide rod is in clearance fit with the outer surface of the fixed guide rod 47 and the outer surface of the rolling guide sleeve 43, so that the movable guide rod 44 can move axially along the fixed guide rod 47; the inner surface of the outer end of the movable guide rod is in threaded connection with the outer surface of the joint 2 and is positioned by a movable guide rod locking nut 3. The outer end of the joint is distributed with a wing joint bearing mounting hole, the outer end of the fixed guide rod is distributed with two fuselage fixed joint bearing mounting holes, and the central line of the assembled wing joint bearing mounting hole is parallel to the central lines of the two fuselage fixed joint bearing mounting holes.

The spring seat 35 is positioned in an annular cavity between the shell 46 and the movable guide rod 44 and is sleeved on the circumferential surface of the movable guide rod, so that the inner surface of the inner end of the spring seat is in clearance fit with the outer surface of the movable guide rod, and the end surface of the outer end of the spring seat is fixedly connected with the inner end surface of the metal capsule base 6 sleeved on the small spring adjusting screw sleeve 5; four lugs evenly distributed on the outer circumference of the middle part of the spring seat are respectively embedded into four sliding grooves on the inner surface of the other end of the shell 46, so that the sliding grooves are in clearance fit, and the spring seat can only move axially along the sliding grooves. The large spring 45 is sleeved on the outer circumferential surfaces of the movable guide rod 44 and the fixed guide rod 47, the end surface of one end of the large spring is attached to the inner end surface of the connecting disc 34 on the fixed guide rod, the other end of the large spring is located in an annular cavity between the outer circumferential surface of the small-diameter end of the spring seat and the inner surface of the shell 46, and the end surface of the end of the large spring is attached to the outer end surface of the middle part of the spring seat 35. The small spring 39 is positioned in a circular cavity between the inner surface of the spring seat and the outer surface of the movable guide rod 44 and is sleeved on the movable guide rod; the end face of the small spring is attached to the inner end face of the small diameter end of the spring seat, and the other end of the small spring is attached to the inner end face of the small spring adjusting threaded sleeve 5 which is sleeved at one end, connected with the joint 2, of the fixed guide rod 47. The small spring adjusting taper sleeve 37 is positioned in the small diameter end of the spring seat, and four arc-shaped inserting blocks on the small spring adjusting taper sleeve are respectively installed in four arc-shaped inserting grooves on the end face of the small diameter end of the spring seat and are fastened outside the spring seat through round nuts 41. The large spring adjusting taper sleeve 38 is sleeved on the outer surface of the small diameter end of the spring seat, and one end of the large spring adjusting taper sleeve is fixed on the outer end surface of the middle part of the spring seat. One end of the supporting sleeve 36 is sleeved on the outer surface of the inner end of the small spring adjusting screw sleeve 5 and is fixed on the inner end surface of the metal diaphragm box 9; the outer surface of the flange of each arc-shaped supporting plate end at the other end of the supporting sleeve 36 is respectively contacted with the inner surface of the large spring adjusting taper sleeve 38, and the inner surface of each flange is respectively contacted with the outer surface of the small spring adjusting taper sleeve 37. When the air pressure controlled by the pressure regulating valve is changed, the metal film box contracts in different degrees, so that the supporting sleeve 36 is driven to move axially, the expansion amount of the small spring adjusting taper sleeve and the expansion amount of the large spring adjusting taper sleeve are changed, and the rigidity of the small spring 39 and the rigidity of the large spring 45 are changed. The metal diaphragm box 9 is fixed in an annular cavity between the inner surface of the large-diameter end of the spring seat and the outer surface of the small spring adjusting screw sleeve 5 through a metal diaphragm box base 6.

When the airplane wing sweep control device works, the aerodynamic resistance load of the wing is transmitted to the movable guide rod 44 through the joint 2, and the large spring and the small spring are compressed to deform gradually, so that the joint 2 is positioned at different positions, and the control of different sweep angles is realized.

The spring seat adjusting screw 33 is fitted around the outer circumferential surface of the large-diameter end of the spring seat 37, and the outer circumferential surface of the small-diameter end of the spring seat adjusting screw is screwed to the inner surface of the end of the housing 46. A sealing felt 11 is installed between the inner circumferential surface of the spring seat adjusting screw and the outer circumferential surface of the spring seat 37.

The metal diaphragm box base 6 is fixedly connected with a guide pipe, and the guide pipe is communicated with the inner cavity of the metal diaphragm box 9 after the main valve core 32 of the pressure regulating valve.

The pressure regulating valve is positioned outside one end of the shell 46 connected with the spring seat adjusting threaded sleeve 33. The pressure regulating valve comprises a main valve body 31, a pilot valve body 28, a main valve core 32, a pilot valve seat 29, a pilot valve needle 27, a spring, a pilot valve cover 19, an air guide pipe 25 and a high-pressure air tank 24. Wherein: the pilot valve seat 29 is positioned in the mounting hole at one end of the pilot valve body 28, the pilot valve needle 27 is arranged in a groove at the center of the end face at the other end of the pilot valve body, and the cover groove is sealed by the pilot valve cover 19; the conical end of the guide valve needle is inserted into a central hole on the guide valve seat; a reinforcing plate 21 is fixed to the outer end face of the pilot valve needle end plate. The central portion of the diaphragm 23 is secured between the reinforcement plate and the pilot valve needle end plate by rivet 22 so that two separate cavities are formed between the reinforcement plate and the pilot valve needle end plate; when the pressure difference of the gas in the two chambers changes, the membrane drives the guide valve needle to move.

The spring is divided into an upper spring 20 and a lower spring 26, the lower spring 26 is sleeved on the outer circumferential surface of the pilot valve needle 27, one end of the lower spring is attached to the inner end face of the large-diameter section of the pilot valve needle, and the other end of the lower spring is attached to the groove bottom face of the groove; the upper spring 20 is located at the outer end of the pilot valve needle and has one end attached to the inner end surface of the pilot valve cap 19 and the other end attached to the outer end surface of the reinforcement plate 21.

The main valve body 31 is mounted on the side surface of the pilot valve body 28 at the end having the pilot valve seat 29. The main valve core 32 is positioned in the main valve body, and the outer circumferential surface of the large-diameter end of the main valve core is in clearance fit with the inner surface of the main valve body, and the outer circumferential surface of the small-diameter end of the main valve core is in clearance fit with the groove wall of the circumferential surface of the pilot valve body; two ends of the small hole in the center of the main valve core are respectively communicated with the small hole in the main valve body and the small hole at the bottom of the groove of the pilot valve body. A spring is placed in an inner hole of the small-diameter end of the main valve body. The high pressure air tank 24 is communicated with the main valve body through an air duct 25, and introduces high pressure air into the main valve core lower chamber in the main valve body 15 to form a main air flow channel.

One end of the joint 2 is a movable guide rod connecting end, is installed in a central hole at one end of the movable guide rod 44 through threads, and is fastened through a movable guide rod locking nut 3. The other end of the joint 2 is a connecting end of a wing transmission rod; the connecting end of the wing transmission rod is in a rectangular block shape, and the surface of the connecting end of the wing transmission rod is provided with a bearing mounting hole for mounting a wing connecting joint bearing 1. And the central line of the bearing mounting hole is perpendicular to the extension line of the central line of the joint. And the connecting end of the movable guide rod and the connecting end of the wing transmission rod are in smooth transition.

The small spring adjusting screw sleeve 5 is a hollow revolving body with the inner circumferential surface being step-shaped. The inner circumferential surface of the small inner diameter section of the small spring adjusting threaded sleeve is in threaded fit with the small outer diameter section of the movable guide rod 44 and is locked by the locking nut 4, so that the adjusting threaded sleeve is prevented from loosening; the inner diameter of the other end of the small spring adjusting screw sleeve is slightly larger than the diameter of the small spring so as to install the small spring inside; the aperture of the middle part of the small spring adjusting screw sleeve is slightly larger than the outer diameter of the working section of the movable guide rod 44, and the small spring adjusting screw sleeve and the working section of the movable guide rod are in clearance fit. The outer surface of the small spring adjusting screw sleeve 5 is in clearance fit with the inner surface of the externally sleeved support sleeve 36 and is sealed by the sealing felt 13, so that external foreign matters are prevented from entering the spring cavity. During assembly, one end of the small spring adjusting screw sleeve 5, which is slightly larger than the diameter of the small spring, is arranged in the supporting sleeve 36 and sleeved on the outer circumferential surface of the working section of the movable guide rod 44 to press the small spring 39.

The metal diaphragm box mounting seat 6 is sleeved on the outer circumferential surface of the small spring adjusting screw sleeve 5, and the small spring adjusting screw sleeve are in clearance fit; the inner end face of the metal diaphragm box mounting seat is attached to the outer end face of the spring seat 35 and fixedly connected with the spring seat through a screw 7.

The metal film box 9 is sleeved on the outer circumferential surface of the small spring adjusting screw sleeve 5, and the small spring adjusting screw sleeve are in clearance fit. The outer end face of the metal film box 9 is fixed on the inner end face of the metal film box mounting seat 6 through a screw 8, and the inner end face of the metal film box 9 is fixed on the outer end face of the supporting sleeve 36 through a screw 10. The metal diaphragm capsule 9 is a contractible annular thin-walled piece and is formed by sleeving two layers of axially foldable paper lanterns together.

The main valve seat 15 is a hollow revolving body with an end cover at one end. The inner surface of the end cover is a boss protruding axially, a conduit mounting hole penetrating axially is arranged in the center of the boss, and the inner end orifice of the mounting hole is conical and matched with the conical section on the main valve core 32. The main valve seat has a radial through hole on the circumference of the end cap for installing the air duct 25. The end face of the outlet end of the main valve seat 15 is stepped, and a positioning spigot matched with the outer surface of the pilot valve body 28 is formed.

The pilot valve cover 19 is disc-shaped, and a groove is formed in the center of the end face of one end of the pilot valve cover, is matched with the pilot valve body and is used for placing the upper spring 20. The outer edge of the guide valve cover is evenly distributed with connecting holes.

The diaphragm 23 is a disc-shaped rubber piece, and the outer edge of the diaphragm is in a plane circular ring shape so as to meet the sealing requirement in clamping. The diaphragm middle portion is corrugated to provide a large deformation margin.

The guide valve needle 26 is cylindrical, one end is a disk riveted with the membrane, the other end is a needle rod, and the front end of the needle rod is a conical needle head. The needle head is in clearance fit with the central hole of the guide valve body and forms a guide valve part with the opening on the guide valve seat so as to control the communication and the separation of the inlet and outlet pressures of the main valve core.

The main body of the pilot valve body 28 is rectangular in shape so as to be fitted and connected to the main valve seat 15. The circular end plate is matched with the pilot valve cover at one end of the main body, a groove is formed in the center of the outer end face of the circular end plate, and a through hole of a pilot valve needle rod extending along the length direction of the pilot valve body is formed in the center of the groove. The geometric center of the other end of the pilot valve body 28 is provided with a mounting hole for the thread of the pilot valve seat 29. The pilot valve seat mounting hole is coaxial with and communicated with the through hole of the pilot valve needle rod. The outer surface of the main body side of the pilot valve body 28 has a sleeve projecting therefrom, and the inner diameter of the sleeve is in clearance fit with the outer circumferential surface of the small outer diameter end of the main valve element 32.

One end of the main valve core 32 is a cylindrical section matched with a sleeve on the pilot valve body, and the other end is a conical section; and a disc is arranged between the cylindrical section and the conical section, and the outer surface of the disc is in clearance fit with the inner surface of the small-diameter hole of the main valve seat. The inner diameter of the cylindrical section is slightly larger than the outer diameter of the main valve spring 30. The conical section is in sealing fit with the inner end of the mounting hole on the main valve seat 15; the center of the conical section is provided with an air hole which is axially communicated, so that the inlet and the outlet of the main valve can be controlled to generate differential pressure, and the outlet pressure of the main valve can be controlled.

The spring seat adjusting screw sleeve 33 is a hollow revolving body. The spring seat adjustment screw 33 has an inner diameter that is the same as the outer diameter of the large diameter end of the spring seat 35. The outer circumferential surface of the spring seat adjusting screw sleeve is stepped, and the outer surface of one end with large outer diameter is processed into an octagon shape, so that the spring seat adjusting screw sleeve is convenient to screw; the outer circumferential surface of the end with the small outer diameter is a thread surface matched with the inner surface of the shell.

The spring seat 35 is a stepped sleeve, and is divided into a large-diameter section and a small-diameter section. The port of the large-diameter section end of the spring seat is open, and the port of the small-diameter section end of the spring seat is provided with an end plate. The inner diameter of the large-diameter end is the same as the outer diameter of the metal diaphragm box base 6; the small diameter end has an end plate and the inner diameter of the small diameter end is the same as the maximum outer diameter of the small spring adjustment taper sleeve 37. Four radially protruding bosses are uniformly distributed on the outer circumferential surface of the spring seat and are positioned at the step in the middle of the outer circumferential surface of the spring seat; each boss corresponds to four grooves evenly distributed on the circumferential surface of the shell 46, and the bosses and the grooves are matched with each other in a clearance mode. A through hole in clearance fit with the outer circumferential surface of the movable guide 44 is provided in the center of the small diameter end face of the spring seat. Four arc through grooves are formed in the end face of the small-diameter end of the spring seat and are uniformly distributed around the through holes, so that the arc strip end of one end of the small spring adjusting taper sleeve 37 penetrates through the end plate of the spring seat from each arc through groove and is fixed by a round nut 41. 4 slots matched with the insertion blocks of the large spring adjusting taper sleeve 38 are uniformly distributed on the outer end face of the middle part of the spring seat 35; the inner side of the slot is provided with a mounting hole for a large spring adjusting taper sleeve fixing screw 14. Three trapezoidal grooves extending to the end of the small-diameter section along the axial direction are uniformly distributed on the end surface between the large-diameter section and the small-diameter section, and the shape of the inner cavity of each trapezoidal groove is matched with the appearance of each support rod on the support sleeve 36 and is used as a sliding groove for the movement of each support rod. Screw mounting holes are uniformly distributed on the end face of the middle step of the spring seat 35 and used for mounting the large spring adjusting taper sleeve 38.

The spring retainer 35 fits within the annular cavity between the housing 46 and the movable guide 44, and the four flanges are in clearance fit with the housing recesses to prevent rotation of the spring retainer. A large spring 45 is arranged in a circular cavity between the outer side of the spring seat and the shell, and a small spring 39 is arranged in a circular cavity between the inner side of the spring seat and the movable guide rod 44. A large spring adjusting taper sleeve 38 is fixed in a spring seat of the large spring, and a small spring adjusting taper sleeve 37 is fixed on an inner end face of an end plate of the spring seat. The amount of deformation of the inner conical surface of the large spring adjustment cone 38 and the amount of deformation of the outer conical surface of the small spring adjustment cone 37 are determined by the axial position of the annular segment of the brace 36. The brace is connected with the metal bellows 6.

The supporting sleeve 36 is cylindrical, and one end of the supporting sleeve is connected with the metal diaphragm box 9 through a screw; the other end of the flange extends out to a certain thickness and is respectively attached to the outer conical surface of the small spring adjusting taper sleeve 37 and the inner conical surface of the large spring adjusting taper sleeve 38 on the inner side, so that the taper is forced to change, and the actual deformation turns of the small spring and the large spring are controlled. In order to realize the overlapping with the spring seat in space, the bearing mounting end of the supporting sleeve 36 is annular, and the other end of the supporting sleeve is axially divided into three arc slats; the three arc strips extend into the annular space of the spring seat 35 respectively, and contact with the inner surface of the large spring adjusting taper sleeve 38 and the outer conical surface of the small spring adjusting taper sleeve 37 through the outer surface and the inner surface of the flange radially protruding from the end surface of each arc strip. The inner surface of the support sleeve matched with the small spring adjusting screw sleeve is provided with an installation groove of a support sleeve sealing felt ring 13.

The small spring adjusting taper sleeve 37 is in a thin-wall cylindrical shape and is divided into a connecting section, a taper section and a deformation section, wherein the taper section and the deformation section are connected through the connecting section, and the small diameter end of the taper section is connected with the connecting section. The taper of the taper section is 10 degrees, and the maximum outer diameter is the same as the inner diameter of the support sleeve 36. Three separation grooves are formed in the axial direction of the conical section, extend from the end head of the conical section to the joint of the conical section and the connecting section, and divide the conical section into three arc plates in the axial direction. The inner surface of each block of the conical section is a helical surface, and the pitch of the helical surface is equal to 10 mm. The outer diameter of the deformation section is equal. In order to realize the connection with the spring seat, four deformation grooves with the width of 10mm are formed in the axial direction of the deformation section, the deformation grooves extend from the end of the deformation section to the joint of the deformation section and the connection section, the deformation section is axially divided into four arc-shaped strips, and the arc-shaped strips can penetrate through the arc-shaped grooves in the spring seat and are fixed through round nuts. The outer surface of each arc-shaped lath of the deformation section is a thread surface. The deformation section can be sufficiently deformed after being pressed.

The large spring adjustment taper sleeve 38 is a thin-walled cylinder and is composed of a circular ring section and a tapered section. And connecting screw holes are distributed on the end surface of the circular ring section. The taper of the conical section is 10 degrees. The outer surface of the conical section is a helical surface, the pitch of the helical surface is 15mm, and the inner surface of the conical section is in contact with the outer rim of the brace 36, wherein the pitch of the helical surface is the same as the lead of the pre-compressed large spring. In order to ensure that the cone section can be fully deformed after being pressed, three uniformly distributed deformation grooves are axially processed on the cone section.

One end of the small spring 39 is sleeved in the annular space between the spring seat 35 and the movable guide rod 44 and corresponds to the small spring adjusting taper sleeve 37 on the outer cylinder of the small spring, and the other end is sleeved in the annular space between the small spring adjusting screw sleeve 5 and the movable guide rod 44. One end face of the small spring 39 is attached to the end face of the inner side of the spring seat 35, and the other end of the small spring 39 is attached to the inner end face of the small spring adjusting screw sleeve 5.

One end of the large spring 45 is sleeved in the annular space between the spring seat 35 and the shell 46, the other end of the large spring is sleeved on the outer circumferential surface of the fixed guide rod 47, one end surface of the large spring is attached to the end surface of the inner side of the outer end of the spring seat, and the inner cylindrical surface of the large spring on the side corresponds to the large spring adjusting taper sleeve 38. The other end face of the large spring is attached to the inner end face of the fixed guide rod 47 fixed to one end of the housing 46.

The rolling guide 43 includes a holder and a rolling steel ball. The inner diameter of the retainer is larger than the outer diameter of the section where the fixed guide rod 47 is matched with the retainer; the aperture of the through holes on the end faces of the two ends of the retainer is slightly larger than the outer diameter of the matching section of the fixed guide rod 47, and the fixed guide rod are in clearance fit. A plurality of rolling steel balls are embedded on the retainer of the rolling sleeve; the surface of the rolling steel ball is in contact with the inner surface of the fixed guide 47 to reduce frictional resistance in the axial movement of the movable guide 44 and to function as an auxiliary bearing.

The movable guide rod 44 is circular, the outer circumferential surface of the movable guide rod is stepped, the circumferential surface of the small outer diameter section at one end is a thread surface which is used for being matched with the internal thread of the small spring adjusting screw sleeve 5 and the internal thread of the small spring adjusting screw sleeve locking nut 4, and the other end is a radially protruding limiting boss; the middle part of the movable guide rod is a working section of the movable rod, and the working section of the movable rod is sleeved with a large spring 45, a small spring 39, a spring seat 35 and a small spring adjusting threaded sleeve 5. The inner diameter of the movable guide rod 44 is in clearance fit with the outer diameter formed by the balls fixed on the rolling guide sleeve 43 and the outer diameter of the working section of the fixed guide rod 47; rolling friction is formed between the movable guide rod and the balls of the rolling guide sleeve so as to reduce the friction resistance between the movable guide rod and the fixed guide rod. The inner circumferential surface of the small outer diameter section of the movable guide rod is an internal thread surface connected with the joint 2.

The shell 46 is in a circular tube shape, and internal threads are formed on the inner surfaces of two ends of the shell and are respectively connected with the external thread surfaces of the fixed guide rod 47 and the spring seat adjusting threaded sleeve 11. Wherein, the inner surface of the side matched with the spring seat adjusting screw sleeve 11 is provided with four axial grooves which are used for matching with the flange of the spring seat 35 and limiting the rotation of the spring seat 35.

The circumferential surface of the fixed guide rod 47 is step-shaped, wherein the diameter of the small-diameter end at one end of the fixed guide rod is slightly smaller than the minimum inner diameter formed by the balls on the rolling guide sleeve; the circumferential surface of the end of the fixed guide rod which is matched with the rolling guide sleeve is a thread surface for mounting the nut 42. The large diameter end of the other end of the fixed guide rod is the rod body of the guide rod, the end of the outer end of the rod body is provided with a connecting disc which protrudes radially, and the circumferential surface of the connecting disc is a threaded surface which is matched with the internal thread of the shell 46. The end face of the outer end of the rod body is provided with a connecting plate which extends axially, a bearing mounting hole of the fuselage fixed joint is formed in the connecting plate, and the center line of the bearing mounting hole of the fuselage fixed joint after assembly is parallel to the center line of the bearing mounting hole of the wing connecting joint of the joint at the other end.

Example 2

The embodiment is a method for controlling the sweepback angle of the wing based on the combined elastic self-adaptive wing sweepback varying mechanism, and the specific process is as follows:

The wing transmission rod is fixedly connected with a joint 2 on the combined elastic self-adaptive wing sweepback changing mechanism through a bearing 1, and a fuselage joint is connected with a fixed guide rod 47 on the combined elastic self-adaptive wing sweepback changing mechanism through two bearing supports, so that pneumatic resistance on the wing is transmitted to a movable guide rod 44 through the joint 2, further under the action of the supporting reaction force of two springs, and finally supported to a fuselage structure through the two bearings by the fixed guide rod 47. The position of the movable guide rod 44 is determined by the compression amount of the large and small springs, and finally the sweepback angle of the wing is controlled.

the small spring is used for adjusting the threaded sleeve 5 to enable the pretightening force of the small spring to reach the aerodynamic resistance with the flight speed of 0.4 Mach; the pretightening force of the large spring is controlled to be the pretightening force when the small spring is completely compressed by adjusting the threaded sleeve 11 through the spring seat. The pre-tightening force of the small spring when the small spring is completely compressed is determined by design. Reasonably determining the rigidity and initial pretightening force of an upper spring 20 and a lower spring 26 on two sides of a pilot valve diaphragm 23 of a pressure regulating valve in the combined elastic self-adaptive wing sweepback mechanism; the determined initial pretightening force is required to meet the condition that the pilot valve is fully opened under the ground condition; along with the change of flying height, the pilot valve is linearly closed to be small, the diaphragm 23 moves to the side of the pilot valve cover 19 to the limit position, the pilot valve needle 26 is driven to be opened to the maximum, the pilot valve is in a full-open state, the gas pressure behind the adjusted main valve core is the maximum pressure, the controlled metal diaphragm box 9 is in a full-expansion state, the support sleeves 36 are all in the limit position towards the fixed guide rod 47, the support sleeves 36 are pushed to the limit position at the side of the fixed guide rod 47, the large spring adjusting taper sleeve 38 is fully contracted, and the number of deformable turns of the large spring 45 becomes the minimum; meanwhile, the small spring adjusting taper sleeve 37 is fully opened, and the deformable number of turns of the small spring 39 becomes maximum. Thus, the stiffness of the small spring 39 is relatively minimal and the stiffness of the large spring 45 is relatively maximal.

And 3, controlling when the flight Mach number is less than 0.4:

when the flight Mach number is less than 0.4, the aerodynamic resistance is always less than the pretightening force of the spring, the spring cannot be pushed to compress, and the sweep angle of the wing in the flight speed range is the designed initial angle. In this embodiment, the initial angle is 10 °.

And 4, controlling when the flight Mach number is larger than 0.4:

when the flight mach number is larger than 0.4, the spring in the wing combination elastic self-adaptive wing sweepback mechanism starts to be compressed to enable the movable guide rod 44 to move towards the fixed guide rod 47 side, and the controlled wing sweepback angle is changed into two sections:

i first section

When the flying height of the airplane is less than 4000 meters: when the Mach number is increased from 0.4 to less than 0.6, the small spring in the combined elastic adaptive wing sweepback mechanism is compressed, so that the joint 2 moves towards the fixed guide rod side of the adaptive wing sweepback mechanism, and the wing sweepback angle is controlled to be increased from 10 degrees to 20 degrees.

When the flying height of the airplane is more than or equal to 4000 meters and less than or equal to 10000 meters: the external air pressure is reduced, so that the pressure on the pilot valve side of the pressure regulating valve diaphragm 23 in the combined elastic self-adaptive wing sweepback mechanism is reduced, the pilot valve moves towards the pilot valve side under the action of the pressure difference on two sides of the diaphragm, the pilot valve is closed, the pressure above and below the main valve core 32 is changed, the main valve core is also closed, and the gas pressure after the main valve is controlled to be gradually reduced. So that the metal bellows is contracted in the axial direction to drive the brace 36 to move toward the connector 2. Make little spring adjustment taper sleeve 37 shrink to control part little spring 39 and adjust the laminating of taper sleeve 37, make little spring 39 deformable number of turns reduce, increase the rigidity of little spring control section. Meanwhile, the large spring adjusting taper sleeve 38 gradually expands under the elastic action of the large spring adjusting taper sleeve, so that the number of fitting circles of the large spring 45 and the large spring adjusting taper sleeve is reduced, the actual number of deformation circles of the large spring 45 is increased, and the rigidity of the large spring control section is reduced. As mach number increases from 0.4, the slope of the controlled sweep angle change increases as the small spring is compressed, compared to heights below 4000 meters, because the small spring 17 stiffness increases, until the flight speed is greater than 0.6, the small spring will be fully compressed. In the process, the moving distance of the support sleeve 36 depends on the air pressure change caused by the flying height, the higher the flying height is, the smaller the air pressure is, the smaller the pilot valve is closed, the longer the distance for controlling the support sleeve 36 to move towards the connector 2 is, the more the rigidity of the small spring 39 is increased, the higher the flying speed when the sweepback angle change of the corresponding wing is turned is, and the smaller the sweepback angle when the wing is turned is, namely, the range of about 20 degrees to 16 degrees. That is, the higher the flying height, the higher the flying speed at which the sweep angle inflection occurs.

When the flying height of the airplane is more than 10000 meters: the external air pressure is reduced to be very small, so that the pressure on the pilot valve side of the pressure regulating valve diaphragm 23 in the combined elastic self-adaptive wing sweepback mechanism is reduced, the pilot valve moves towards the pilot valve side under the action of the pressure difference on two sides of the diaphragm, the pilot valve is closed, the pressure above and below the main valve core 32 is changed, the main valve core is also closed, and the gas pressure after the main valve is controlled to be gradually reduced. The metal film box is contracted along the axial direction, the supporting sleeve 36 is driven to move to the other side limit position of the stroke of the supporting sleeve in the direction of the connector 2, the small spring adjusting taper sleeve 37 is forced to be completely contracted, and the deformable number of turns of the small spring 39 is reduced to the minimum; at the same time, the large spring adjustment cone 38 is fully expanded, maximizing the actual number of turns of the large spring 45. When the mach number is increased from 0.4, the slope of the change of the sweep angle controlled when the small spring is compressed increases as compared to a height of 10000 meters or less, because the stiffness of the small spring 39 increases, until the flying speed reaches 0.8, the small spring 39 will be fully compressed, corresponding to a sweep angle of 16 °.

II second section

When the flying height of the airplane is less than 4000 meters: when the Mach number is increased from 0.6 to less than 0.9, the small spring in the combined elastic self-adaptive wing variable sweepback mechanism is completely compressed, the large spring starts to be compressed, so that the joint 2 continues to move, the sweepback angle is controlled to continue to increase according to the slope controlled by the large spring, and the corresponding relation between the flight Mach number from 0.6-0.9 and the sweepback angle of the wing from 20 degrees to 60 degrees is realized.

When the flying height of the airplane is more than or equal to 4000 meters and less than or equal to 10000 meters: the change relation of the aircraft sweepback angle along with the change of the flying speed changes along with the change of the flying height, for example, when the corresponding sweepback angle is increased from 20 degrees to 60 degrees, the change of the flying speed is Mach 0.6 to 0.9; when the corresponding sweepback angle is increased from 16 degrees to 60 degrees at 10000 meters, the change of the flying speed is Mach 0.8 to 0.9; between these two altitudes, the starting angle of the sweep angle varies linearly between 20 ° and 16 °, with corresponding variations in flight speed between mach 0.6 and mach 0.8. Namely: the higher the flying height, the smaller the starting angle of the sweep angle, and the higher the starting speed of the flying speed. The process is controlled by the movement of the brace controlled by the pressure regulator. Since the distance that the brace 36 moves depends on the change of the air pressure caused by the flying height, the higher the flying height is, the longer the distance that the brace 36 moves towards the joint 2 is controlled, the more the rigidity of the large spring 39 is reduced, and the slower the change of the wing sweep angle along with the flying speed is. The large control spring 45 in the section has more deformation turns than 4000 meters, so the control slope of the flight speed and the sweepback angle is smaller.

Claims

1. A combined elastic self-adaptive wing sweepback-changing mechanism is characterized by comprising an outer shell, a metal diaphragm capsule, a spring seat, a small spring, a rolling guide sleeve, a movable guide rod, a large spring, a fixed guide rod and a pressure regulating valve; the fixed guide rod is positioned in the center in the outer shell, and the outer circumferential surface of the connecting disc at one end of the fixed guide rod is in threaded connection with the inner surface at one end port of the outer shell; the rolling guide sleeve is sleeved at the other end of the fixed guide rod; the inner end of the movable guide rod is sleeved on the fixed guide rod and the rolling guide sleeve, and the inner surface of the movable guide rod is in clearance fit with the outer surface of the fixed guide rod and the outer surface of the rolling guide sleeve; the inner surface of the outer end of the movable guide rod is in threaded connection with the outer surface of the joint; the spring seat is sleeved on the circumferential surface of the movable guide rod, and the large spring is sleeved on the outer circumferential surfaces of the movable guide rod and the fixed guide rod; the small spring is sleeved on the movable guide rod, and the metal diaphragm capsule is communicated with the pressure regulating valve through a guide pipe;

the pressure regulating valve is positioned outside the outer shell; the pressure regulating valve comprises a main valve body, a guide valve body, a main valve core, a guide valve seat, a guide valve needle, a spring, an air guide pipe, a membrane and a high-pressure air tank; wherein: the guide valve seat is positioned in the mounting hole at one end of the guide valve body, and the guide valve needle is mounted in a groove in the center of the end face at the other end of the guide valve body; the conical end of the guide valve needle is inserted into a central hole on the guide valve seat;

a reinforcing plate is fixed on the outer end face of one end plate of the pilot valve needle; the central part of the membrane is fixed between the reinforcing plate and the needle end plate of the pilot valve, so that two isolated cavities are formed between the reinforcing plate and the needle end plate of the pilot valve; the spring is divided into a spring I and a spring II, the spring II is sleeved on the outer circumferential surface of the pilot valve needle, one end of the spring II is attached to the inner end face of the end plate of the pilot valve needle, and the other end of the spring II is attached to the bottom face of the groove; the spring I is positioned at the outer end of the pilot valve needle, one end of the spring I is attached to the inner end face of the pilot valve cover, and the other end of the spring I is attached to the outer end face of the reinforcing plate; the main valve body is arranged on the side surface of one end of the guide valve body, which is provided with the guide valve seat; the main valve core is positioned in the main valve body, and the outer circumferential surface of the large-diameter section of the main valve core is in clearance fit with the groove wall of the circumferential surface of the pilot valve body; the conical small-diameter section of the main valve core is in sealing fit with the inner end of the mounting hole on the main valve body; a disc is arranged between the large-diameter section and the small-diameter section of the main valve core, and the outer surface of the disc is in clearance fit with the inner surface of the small-diameter hole of the main valve body; the inner diameter of the large-diameter section is slightly larger than the outer diameter of the main valve spring;

two ends of the small hole in the center of the main valve core are respectively communicated with the small hole in the main valve body and the small hole at the bottom of the groove of the pilot valve body;

a main valve spring is arranged in an inner hole of the large-diameter section of the main valve core; the high-pressure air tank is communicated with the main valve body through an air duct, and high-pressure air is introduced into the lower cavity of the main valve core to form a main air flow channel;

the end face of one end of the groove of the guide valve cover is fixedly connected with the end face of the guide valve body; the outer edge of the diaphragm is clamped between the end face of the pilot valve cover and the end face of the pilot valve body;

the end plate at one end of the pilot valve needle is a disc riveted with the diaphragm, the other end of the pilot valve needle is a needle rod, and the front end of the needle rod is a conical needle head;

the needle head is in clearance fit with the through hole of the guide valve body and forms a guide valve part with the opening on the guide valve seat so as to control the communication and the separation of the inlet and outlet pressures of the main valve core;

the spring seat adjusting screw sleeve is sleeved on the outer circumferential surface of the large-diameter section of the spring seat, and the outer circumferential surface of the small-diameter end of the spring seat adjusting screw sleeve is in threaded connection with the inner surface of the end socket of the outer shell;

the inner circumferential surface of the small inner diameter section of the small spring adjusting screw sleeve is in threaded fit with the small outer diameter section of the movable guide rod; the aperture of the middle part of the small spring adjusting threaded sleeve is slightly larger than the outer diameter of the working section of the movable guide rod, and the small spring adjusting threaded sleeve and the working section of the movable guide rod are in clearance fit; the outer surface of the small spring adjusting screw sleeve is in clearance fit with the inner surface of the externally sleeved support sleeve; the small spring adjusting screw sleeve is arranged in the support sleeve at one end slightly larger than the diameter of the small spring, sleeved on the outer circumferential surface of the working section of the movable guide rod and tightly presses the small spring.

2. The combined elastic self-adaptive wing sweepback-changing mechanism of claim 1, wherein the inner surface of the inner end of the spring seat sleeved on the movable guide rod is in clearance fit with the outer surface of the movable guide rod, so that the end surface of the outer end of the spring seat is fixedly connected with the inner end surface of the metal bellows base sleeved on the small spring adjusting screw sleeve;

four lugs uniformly distributed on the outer circumference of the middle part of the spring seat are respectively embedded into four sliding grooves on the inner surface of the other end of the outer shell, so that the sliding grooves are in clearance fit;

the end face of one end of the large spring is attached to the inner end face of the connecting disc on the fixed guide rod, and the other end of the large spring is located in an annular cavity between the outer circumferential surface of the small-diameter section of the spring seat and the inner surface of the outer shell, and the end face of the large spring is attached to the inner end face of the middle part of the spring seat; the end surface of the small spring is attached to the inner end surface of the small diameter section of the spring seat, and the other end of the small spring is attached to the inner end surface of the small spring adjusting threaded sleeve sleeved at one end, connected with the joint, of the fixed guide rod; the small spring adjusting taper sleeve is positioned in the small-diameter section of the spring seat, and four arc-shaped inserting blocks on the small spring adjusting taper sleeve are respectively arranged in four arc-shaped inserting grooves on the end surface of the small-diameter section of the spring seat; the large spring adjusting taper sleeve is sleeved on the outer surface of the small-diameter section of the spring seat, and one end of the large spring adjusting taper sleeve is fixed on the inner end surface of the middle part of the spring seat; the outer surface of the flange of each arc supporting plate end at the other end of the supporting sleeve is respectively contacted with the inner surface of the large spring adjusting taper sleeve, and the inner surface of each flange is respectively contacted with the outer surface of the small spring adjusting taper sleeve.

3. The combined elastic adaptive wing sweepback mechanism of claim 1, wherein the inner surface of the main valve body is an axially protruding boss, a conduit mounting hole axially penetrating is formed in the center of the boss, and an inner end opening of the mounting hole is conical and matched with the conical section on the main valve core; the circumference of one end of the main valve body, which is provided with an end cover, is provided with a radial through hole for installing an air guide pipe; the end face of the outlet end of the main valve body is in a step shape, and a positioning spigot matched with the outer surface of the pilot valve body is formed.

4. The combined elastic adaptive wing sweepback mechanism of claim 1, wherein the main body of the pilot valve body is cuboid; one end of the main body is provided with a circular end plate matched with the pilot valve cover, the center of the outer end surface of the circular end plate is provided with a groove, and the center of the groove is provided with a through hole of a pilot valve needle rod extending along the length direction of the pilot valve body; a guide valve seat mounting hole is formed in the geometric center of the other end of the guide valve body; the pilot valve seat mounting hole is coaxial with and communicated with the through hole of the pilot valve needle rod; the outer surface of one side of the pilot valve body is provided with a sleeve protruding out of the outer surface, and the inner surface of the sleeve is in clearance fit with the outer circumferential surface of the large-diameter section of the main valve core.

5. The combined elastic adaptive wing sweepback mechanism of claim 1, wherein the port at one end of the large-diameter end section of the spring seat is open, and the port at one end of the small-diameter end section of the spring seat is provided with an end plate; the inner diameter of the large-diameter section of the spring seat is the same as the outer diameter of the metal diaphragm box base; the small-diameter section of the spring seat is provided with an end plate, and the inner diameter of the small-diameter section of the spring seat is the same as the maximum outer diameter of the small-spring adjusting taper sleeve; four bosses protruding in the radial direction are uniformly distributed on the outer circumferential surface of the spring seat, and each boss is positioned at a step in the middle of the outer circumferential surface of the spring seat; each boss corresponds to four grooves uniformly distributed on the circumferential surface of the outer shell; a through hole in clearance fit with the outer circumferential surface of the movable guide rod is formed in the center of the end surface of the small-diameter section of the spring seat; the end surface of the small diameter section of the spring seat is provided with four arc slots which are uniformly distributed around the through hole, so that the arc strip end of one end of the small spring adjusting taper sleeve penetrates through the end plate of the spring seat from each arc slot; 4 slots matched with the insertion blocks of the large spring adjusting taper sleeves are uniformly distributed on the outer end face of the middle part of the spring seat; the inner side of the slot is provided with a mounting hole; three trapezoidal grooves extending to the small-diameter end along the axial direction are uniformly distributed on the end face between the large-diameter end and the small-diameter end, and the shape of the inner cavity of each trapezoidal groove is matched with the appearance of each support rod on the support sleeve and is used as a sliding groove for the movement of each support rod.

6. The combined elastic adaptive wing sweepback-changing mechanism of claim 2, wherein the supporting sleeve is cylindrical, one end of the supporting sleeve is connected with the metal bellows, and the other end of the supporting sleeve is axially divided into three arc slats; the end surfaces of the three arc-shaped strips are provided with flanges protruding in the radial direction, and the outer surfaces and the inner surfaces of the flanges are respectively contacted with the inner surface of the large spring adjusting taper sleeve and the outer conical surface of the small spring adjusting taper sleeve simultaneously.

7. The combined elastic adaptive wing sweepback mechanism of claim 6, wherein the small spring adjusting taper sleeve is in a shape of a thin-walled cylinder and is divided into a connecting section, a conical section and a deformation section, wherein the conical section and the deformation section are connected through the connecting section, and the small diameter section of the conical section is connected with the connecting section; the taper of the taper section is 10 degrees, and the maximum outer diameter of the taper section is the same as the inner diameter of the support sleeve; three separation grooves are formed in the axial direction of the conical section, extend from the end head of the conical section to the joint of the conical section and the connecting section, and divide the conical section into three arc plates in the axial direction; the inner surfaces of the blocks of the conical section are all helicoids, and the screw pitch of the helicoids is equal to 10 mm; the outer diameter of the deformation section is equal; four deformation grooves with the width of 10mm are formed in the axial direction of the deformation section, the deformation grooves extend from the end of the deformation section to the joint of the deformation section and the connecting section, the deformation section is axially divided into four arc-shaped strips, and the arc-shaped strips can penetrate through arc-shaped slots in the spring seat and are fixed through round nuts; the outer surface of each arc-shaped lath of the deformation section is a threaded surface;

the large spring adjusting taper sleeve is in a thin-wall cylindrical shape and consists of a circular ring section and a taper section; connecting screw holes are distributed on the end surface of the circular ring section; the taper of the taper section of the taper sleeve is adjusted to be 10 degrees by the large spring; the outer surface of the conical section of the large spring adjusting taper sleeve is a spiral surface, and the screw pitch on the spiral surface is 15mm, so that the screw pitch is the same as the lead of the pre-compressed large spring; the inner surface of the conical section of the large spring adjusting taper sleeve is contacted with the outer surface of the flange which is radially protruded from the end surface of each arc slat; three uniformly distributed deformation grooves are processed on the conical section along the axial direction.

8. The combined elastic adaptive wing sweepback mechanism of claim 1, wherein the outer circumferential surface of the movable guide rod is stepped, the outer circumferential surface of the small outer diameter section at one end is a thread surface, and the other end is a radially protruding limiting boss; the middle part of the movable guide rod is a working section of the movable rod; the inner diameter of the movable guide rod is in clearance fit with the outer diameter formed by the balls fixed on the rolling guide sleeve and the outer diameter of the fixed guide rod; rolling friction is formed between the movable guide rod and the balls of the rolling guide sleeve; the inner circumferential surface of the small outer diameter section of the movable guide rod is an internal thread surface connected with the joint;

the diameter of the small-diameter section of the fixed guide rod is slightly smaller than the minimum inner diameter formed by the balls on the rolling guide sleeve; the circumferential surface of one end, matched with the rolling guide sleeve, of the fixed guide rod is a threaded surface; the large-diameter section at the other end of the fixed guide rod is a rod body of the guide rod, the end head of the outer end of the rod body is provided with a connecting disk protruding in the radial direction, and the circumferential surface of the connecting disk is a threaded surface matched with the internal thread of the outer shell; the end face of the outer end of the rod body is provided with a connecting plate which extends axially, a bearing mounting hole of the fuselage fixed joint is formed in the connecting plate, and the center line of the bearing mounting hole of the fuselage fixed joint after assembly is parallel to the center line of the bearing mounting hole of the wing connecting joint of the joint at the other end.

9. A method for implementing control by using the combined elastic adaptive wing sweepback mechanism of the claim 1 is characterized by comprising the following specific processes:

step 1, connecting a combined elastic self-adaptive wing sweepback changing mechanism with a fuselage and wings;

the wing transmission rod is fixedly connected with a joint on the combined elastic self-adaptive wing sweepback changing mechanism through a bearing, and a fuselage fixed joint is connected with a fixed guide rod on the combined elastic self-adaptive wing sweepback changing mechanism through two bearing supports;

the small spring is used for adjusting the threaded sleeve to enable the pretightening force of the small spring to reach the aerodynamic resistance with the flight speed of 0.4 Mach; the pretightening force of the large spring is controlled to be the pretightening force when the small spring is completely compressed by adjusting the threaded sleeve through the spring seat; the pretightening force of the small spring when the small spring is completely compressed is determined by design; the determined initial pretightening force is required to meet the requirement that the pilot valve is fully opened under the ground condition; along with the change of flying height, the linear turn-off of the pilot valve is reduced, the diaphragm moves to the side of the pilot valve cover to the limit position, the pilot valve needle is driven to be opened to the maximum, the pilot valve is in a full-open state, the gas pressure behind the adjusted main valve core is the maximum pressure, the controlled metal diaphragm box is in a full-expansion state, and the support sleeves are all in the limit position towards the fixed guide rod; pushing the support sleeve to the limit position on one side of the fixed guide rod, so that the large spring adjusting taper sleeve is fully expanded, and the deformable number of turns of the large spring is minimized; meanwhile, the small spring adjusting taper sleeve is completely opened, and the deformable number of turns of the small spring becomes the maximum;

and 3, controlling when the flight Mach number is less than 0.4:

when the flight Mach number is less than 0.4, all the sweep angles of the wings in the flight speed range are designed initial angles;

and 4, controlling when the flight Mach number is larger than 0.4:

when the flight Mach number is larger than 0.4, the large spring and the small spring in the wing combined elastic self-adaptive wing sweepback changing mechanism start to be compressed at the same time to enable the movable guide rod to move towards the fixed guide rod side, and the controlled wing sweepback angle is changed into two sections: i first section

When the flying height of the airplane is less than 4000 meters: when the Mach number is increased from 0.4 to less than 0.6, a small spring in the combined elastic self-adaptive wing sweep-back mechanism is compressed, so that a joint moves towards one side of a fixed guide rod of the self-adaptive wing sweep-back mechanism, and the wing sweep-back angle is controlled to be increased from 10 degrees to 20 degrees;

when the flying height of the airplane is more than or equal to 4000 meters and less than or equal to 10000 meters: the external air pressure is reduced, the deformable number of turns of the small spring in the combined elastic self-adaptive wing sweepback-changing mechanism is reduced, and the rigidity of the small spring control section is increased; meanwhile, the large spring adjusting taper sleeve gradually contracts under the action of the elasticity of the large spring adjusting taper sleeve, so that the number of joint turns of the large spring and the large spring adjusting taper sleeve is reduced, the actual number of deformation turns of the large spring is increased, and the rigidity of a control section of the large spring is reduced; when the Mach number is increased from 0.4, the change slope of the sweepback angle controlled when the small spring is compressed is increased, and the small spring is completely compressed until the flying speed is more than 0.6; in the process, the moving distance of the support sleeve depends on the air pressure change caused by the flying height, the higher the flying height is, the smaller the air pressure is, the smaller the pilot valve is closed, the longer the distance for controlling the support sleeve to move towards the joint direction is, the more the rigidity of the small spring is increased, the higher the flying speed when the change of the sweepback angle of the corresponding wing is turned is, and the smaller the sweepback angle during turning is, namely 20-16 degrees;

when the flying height of the airplane is more than 10000 meters: the pressure of the side of a diaphragm pilot valve of a pressure regulating valve in the combined elastic self-adaptive wing sweepback changing mechanism is reduced, a main valve core is also closed, and the pressure of gas regulated by a main valve is gradually reduced; the metal diaphragm box contracts along the axial direction to drive the supporting sleeve to move to the limit position of the other side of the stroke of the supporting sleeve in the direction of the joint, the small spring adjusts the taper sleeve to completely contract, and the deformable number of turns of the small spring is reduced to the minimum; meanwhile, the large spring adjustment taper sleeve is completely contracted, so that the actual deformation circle number of the large spring is increased to the maximum; when the mach number is increased from 0.4, compared with the height below 10000 meters, because the rigidity of the small spring is increased, the change slope of the sweepback angle controlled when the small spring is compressed is increased, and until the flying speed reaches 0.8, the small spring is completely compressed, and the corresponding sweepback angle is 16 degrees;

II second section

The sweepback angle change of the wing is controlled through the supporting sleeve;

when the flying height of the airplane is less than 4000 meters: when the Mach number is increased from 0.6 to less than 0.9, the small spring in the combined elastic self-adaptive wing variable sweepback mechanism is completely compressed, the large spring starts to be compressed, so that the joint continues to move, the sweepback angle is controlled to continue to increase according to the slope controlled by the large spring, and the corresponding relation between the flight Mach number from 0.6-0.9 and the sweepback angle of the wing from 20 degrees to 60 degrees is realized;

when the flying height of the airplane is more than or equal to 4000 meters and less than or equal to 10000 meters: at 4000 meters, the corresponding sweepback angle is increased to 60 degrees from the initial angle of 20 degrees, and the flight speed is increased to 0.9 mach from 0.6 mach of the initial speed; at 10000 m, the corresponding sweepback angle is increased from the initial angle of 16 degrees to 60 degrees, and the flight speed is increased from 0.8 of the initial speed to 0.9 mach; when the flying height is 4000-10000 m, the initial angle of the sweepback angle is linearly changed between 20-16 degrees, and the initial speed of the corresponding flying speed is changed between Mach 0.6-0.8;

when the flying height of the airplane is more than 10000 meters: when the Mach number is increased from 0.8 to less than 0.9, the small springs in the adaptive wing sweep-back mechanism are completely compressed, and the large springs are compressed; because the effective deformation turns of the large spring are increased to the maximum and the rigidity of the large spring is reduced to the minimum, the corresponding sweepback angle is 16-60 degrees when the flying speed reaches the Mach number of 0.8-0.9.